CN205049312U - Control surface torgue measurement structure - Google Patents
Control surface torgue measurement structure Download PDFInfo
- Publication number
- CN205049312U CN205049312U CN201520844270.0U CN201520844270U CN205049312U CN 205049312 U CN205049312 U CN 205049312U CN 201520844270 U CN201520844270 U CN 201520844270U CN 205049312 U CN205049312 U CN 205049312U
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- China
- Prior art keywords
- control surface
- wing
- model
- rotating shaft
- balance
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- Expired - Fee Related
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- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The utility model discloses a control surface torgue measurement structure, include and support the pivot on the wing of model aircraft with the control surface, the pivot has the follow the wing extends the entering the first end of the inside of the fuselage of model aircraft and with the second end that the first end is relative, the inside of fuselage is provided with a connection the measurement balance of first end, the centre of control surface is provided with two and exposes the breach of pivot, it stretches into to be provided with two on the wing the breach supports the support arm of pivot. The utility model discloses a control surface torgue measurement structure will measure balance lug connection to the pivot that extends to the control surface in the fuselage, utilize the pivot moment of balance direct measurement control surface, overcome the three -component balance and warp by the wing to influence the defect that measuring error is big, utilize the space in the fuselage to realize the more measurement of high accuracy, the installation and debugging being convenient for the balance and measuring equipment such as cable.
Description
Technical field
The utility model relates in aircraft wind tunnel experiment, for the structure of the control surface stressing conditions of survey aircraft model, and especially a kind of control surface torgue measurement structure.
Background technology
The moment that the control surface of aircraft is subject to by the rotating shaft that catanator overcomes control surface and deflecting, therefore the airplane design stage needs the moment size of the rotating shaft of being measured control surface by wind tunnel test.The basic demand of aircraft to control surface is: control surface can produce enough operating torques, to ensure that aircraft can fly under required state, the time that control surface deflects into required angle is short, to ensure that aircraft has good maneuverability, meet the size that these requirements must know the rotating shaft moment of control surface, to design the booster of suitable control surface.Usually three-component balance and four COMPONENT BALANCE are adopted to measure the moment of control surface in prior art, namely be provided with multiple balance beam be arranged in parallel along control surface length direction interval, according to the distance between the stressing conditions on each balance that measurement obtains and balance, calculate with the product of distance the rotating shaft moment obtaining control surface by stressed.But for the model aircraft of wind tunnel test, because it has reduced doubly a lot relative to prototype, therefore the wing of model aircraft has become very thin, wing distortion will produce very large interference to measurement result, also measurement of correlation cable to be linked together still more, in actual measurement process, the layout of measuring mechanism is often very difficult, have impact on the precision of measurement result.
Utility model content
The technical problems to be solved in the utility model is to provide a kind of control surface torgue measurement structure, to reduce or to avoid problem noted earlier.
Specifically, the utility model provides a kind of control surface torgue measurement structure, for the control surface moment of survey aircraft model in wind tunnel test, described control surface torgue measurement structure comprises the rotating shaft be supported on by described control surface on the wing of described model aircraft, described rotating shaft has and extends into the first end of the inside of the fuselage of described model aircraft and the second end relative with described first end from described wing, and the inside of described fuselage is provided with the measurement balance that connects described first end; The centre of described control surface is provided with the breach that two are exposed described rotating shaft, described wing is provided with two and stretches into the support arm that described breach supports described rotating shaft.
Preferably, the spacing between two breach on described control surface equal described control surface along the length direction of described rotating shaft length 1/3.
Measurement balance is directly connected in the rotating shaft of the control surface extended in fuselage by control surface torgue measurement structure of the present utility model, balance is utilized directly to measure the rotating shaft moment of control surface, overcome three-component balance and be subject to the defect that wing deformation effect measuring error is large, utilize the space in fuselage to realize more high-precision measurement, be convenient to balance and measure the Installation and Debugging of the equipment such as cable.
Accompanying drawing explanation
The following drawings is only intended to schematically illustrate the utility model and explain, does not limit scope of the present utility model.Wherein,
Fig. 1 display be the schematic diagram of control surface torgue measurement structure according to a specific embodiment of the present utility model.
Embodiment
In order to there be understanding clearly to technical characteristic of the present utility model, object and effect, now contrast accompanying drawing and embodiment of the present utility model is described.Wherein, identical parts adopt identical label.
Fig. 1 display be the schematic diagram of control surface torgue measurement structure according to a specific embodiment of the present utility model, as shown in the figure, control surface torgue measurement structure of the present utility model is used for the control surface moment of survey aircraft model in wind tunnel test, wherein, described control surface can be the flaperon, elevating rudder, yaw rudder, front wing etc. of model aircraft.
Control surface torgue measurement structure of the present utility model comprises the rotating shaft 11 be supported on by control surface 1 on the wing 2 of model aircraft, rotating shaft 11 has and extends into the first end of fuselage 3 inside of model aircraft and the second end relative with described first end from wing 2, and the inside of fuselage 3 is provided with the measurement balance 4 that connects first end.That is the utility model proposes a kind of measurement thinking newly according to the defect of prior art, namely, extend in the rotating shaft 11 of the control surface 1 in fuselage by only needing the measurement balance 4 of simple component to be connected to, utilize and measure the rotating shaft moment that control surface 1 directly measured by balance 4, and due to the space in fuselage enough spacious, can realize more high-precision balance design, and the Installation and Debugging of the equipment such as balance and measurement cable are all very convenient.
It is inner that rotating shaft 11 extends to fuselage 3 through wing 2, be connected with at the first end of rotating shaft 11 and measure balance 4, in order to control surface 1 is supported on wing 2, bearing (not shown) is provided with at the two ends of rotating shaft 11, the inner ring of these bearings is fixedly connected with rotating shaft 11, the outer ring supporting construction corresponding on wing 2 is fixedly connected with, and to be supported on by control surface 1 on wing 2 and can 11 freely to rotate around the shaft with this.In a specific embodiment, aerodynamic loading distortion is subject in order to prevent control surface 1, the centre of control surface 1 is provided with the breach 12 that two are exposed rotating shaft 11, wing 2 is provided with two and stretches into the support arm 13 that described breach 12 supports described rotating shaft 11, described support arm 13 also can be arranged the bearing that is connected with rotating shaft 11 to reduce the impact of friction force on measuring accuracy.Indeformable in order to ensure rotating shaft 11, during test, control surface 1 is not acutely shaken, the high precision ball miniature bearing that the bearing of supporting revolving shaft 11 can adopt frictional force square very little, and these bearings can adopt unsealed form, use coal Water Oil Or Gas lubrication, can frictional force be reduced like this.
In a specific embodiment, in order to avoid the discontinuity equalization on two support arms 13 forms extra moment loading, affect measuring accuracy, spacing between two breach 12 on preferred control surface 1 equal control surface 1 along the length direction of rotating shaft 11 length 1/3, the position that namely can set two support arms 13 is positioned at each 1/3 place at the two ends of control surface 1, thus extra warping moment can not be produced due to the deadweight of control surface 1, improve measuring accuracy.
The foregoing is only the schematic embodiment of the utility model, and be not used to limit scope of the present utility model.Any those skilled in the art, the equivalent variations done under the prerequisite not departing from design of the present utility model and principle, amendment and combination, all should belong to the scope of the utility model protection.
Claims (2)
1. a control surface torgue measurement structure, for the control surface moment of survey aircraft model in wind tunnel test, it is characterized in that, described control surface torgue measurement structure comprises the rotating shaft be supported on by described control surface on the wing of described model aircraft, described rotating shaft has and extends into the first end of the inside of the fuselage of described model aircraft and the second end relative with described first end from described wing, and the inside of described fuselage is provided with the measurement balance that connects described first end; The centre of described control surface is provided with the breach that two are exposed described rotating shaft, described wing is provided with two and stretches into the support arm that described breach supports described rotating shaft.
2. control surface torgue measurement structure as claimed in claim 1, is characterized in that, the spacing between two breach on described control surface equal described control surface along the length direction of described rotating shaft length 1/3.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520844270.0U CN205049312U (en) | 2015-10-28 | 2015-10-28 | Control surface torgue measurement structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520844270.0U CN205049312U (en) | 2015-10-28 | 2015-10-28 | Control surface torgue measurement structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205049312U true CN205049312U (en) | 2016-02-24 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520844270.0U Expired - Fee Related CN205049312U (en) | 2015-10-28 | 2015-10-28 | Control surface torgue measurement structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205049312U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107247839A (en) * | 2017-06-08 | 2017-10-13 | 中国航空工业集团公司哈尔滨空气动力研究所 | A kind of low-speed wind tunnel virtual flight flight test vehicle design methods |
| CN111504596A (en) * | 2020-04-07 | 2020-08-07 | 中国空气动力研究与发展中心低速空气动力研究所 | Hinge moment balance |
-
2015
- 2015-10-28 CN CN201520844270.0U patent/CN205049312U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107247839A (en) * | 2017-06-08 | 2017-10-13 | 中国航空工业集团公司哈尔滨空气动力研究所 | A kind of low-speed wind tunnel virtual flight flight test vehicle design methods |
| CN107247839B (en) * | 2017-06-08 | 2020-04-21 | 中国航空工业集团公司哈尔滨空气动力研究所 | Design method of low-speed wind tunnel virtual flight test airplane model |
| CN111504596A (en) * | 2020-04-07 | 2020-08-07 | 中国空气动力研究与发展中心低速空气动力研究所 | Hinge moment balance |
| CN111504596B (en) * | 2020-04-07 | 2020-12-29 | 中国空气动力研究与发展中心低速空气动力研究所 | Hinge moment balance |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20160224 Termination date: 20171028 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |